Turbocharger compressor noise reduction system and method

Patent metadata

Field	Value
Publication number	US-9303561-B2
Application number	US-201213528622-A
Country	US
Kind code	B2
Filing date	Jun 20, 2012
Priority date	Jun 20, 2012
Publication date	Apr 5, 2016
Grant date	Apr 5, 2016

Abstract

A turbocharger and a method are disclosed. The turbocharger includes a casing having an inlet end and an outlet end. A flow passage within the casing may have a substantially continuous inner surface and may be configured to pass inlet air from the inlet end to the outlet end. A compressor wheel may be located in the casing and may have at least one main blade and may be configured to rotate within the casing to compress the inlet air. A flow disrupting feature on the casing may be configured to disrupt the continuity of the inner surface and may be located at a leading edge of the at least one main blade. The flow disrupting feature may be closed to upstream communication with the flow passage except via the flow passage.

First claim

The invention claimed is:

1. A turbocharger comprising:
a casing having an inlet end and an outlet end;
a flow passage within the casing having a substantially continuous inner surface and configured to pass inlet air from the inlet end to the outlet end;
a compressor wheel located in the casing having at least one main blade and configured to rotate within the casing to compress the inlet air; and
an annular flow disrupting feature on the casing configured to disrupt the continuity of the inner surface located at a leading edge of the at least one main blade and wherein the flow disrupting feature is closed to upstream communication with the flow passage except via the flow passage, wherein a leading edge surface of the flow disrupting feature splays radially outward, in a direction away from a central axis of the casing, at an obtuse angle from a surface of the casing.

2. The turbocharger of claim 1 , wherein a majority of the flow disrupting feature is located upstream from the leading edge of the at least one main blade.

3. The turbocharger of claim 1 , wherein a trailing edge of the flow disrupting feature is located a distance from the leading edge of the at least one main blade.

4. The turbocharger of claim 1 , wherein at least a portion of the flow disrupting feature is located upstream from the leading edge of the at least one main blade.

5. The turbocharger of claim 1 , wherein a downstream portion of the flow disrupting feature, between the leading edge surface and a trailing edge of the flow disrupting feature is angled radially inward from a downstream end of the leading edge surface, in a direction toward the central axis of the casing.

6. The turbocharger of claim 5 , wherein an acute angle is formed between the leading edge surface of the flow disrupting feature and the downstream portion of the flow disrupting feature.

7. The turbocharger of claim 5 , wherein the downstream portion of the flow disrupting feature includes a step in the inner surface.

8. The turbocharger of claim 7 , wherein a step face of the step is arranged at an angle with an incoming flow of inlet air.

9. The turbocharger of claim 7 , wherein the step reduces a cross-sectional area of the flow passage.

10. The turbocharger of claim 9 , further comprising a swirl generating device upstream from the step configured to impart a swirl to a flow of the inlet air.

11. The turbocharger of claim 5 , wherein the flow disrupting feature continuously transitions from upstream to downstream in the casing, the leading edge surface of the flow disrupting feature forming an upstream transitional portion and the downstream portion of the flow disrupting feature forming a downstream transitional portion.

12. The turbocharger of claim 11 , wherein one or both of the upstream transitional portion and the downstream transitional portion include filleted corners.

13. The turbocharger of claim 11 , wherein one or both of the upstream and downstream transitional portions are spline surfaces.

14. The turbocharger of claim 1 , wherein a trailing edge of the flow disrupting feature is located substantially in line axially to the leading edge of the at least one main blade.

15. The turbocharger of claim 1 , wherein the compressor wheel also includes one or more splitter blades having respective one or more leading edges each located downstream from the leading edge of the at least one main blade.

16. A turbocharger comprising:
a casing, wherein a most upstream portion of the casing is angled inward in a direction towards a central axis of the casing, and where a portion of the casing located downstream of the most upstream portion of the casing is parallel with the central axis of the casing;
a compressor wheel located in the casing having at least one main blade and rotatable within the casing, about the central axis, to compress inlet air;
a flow passage within the casing having an inner surface configured to pass the inlet air from an inlet end to an outlet end; and
an annular flow disrupting feature on the casing, the annular flow disrupting feature located at a leading edge of the at least one main blade and downstream of the portion of the casing parallel with the central axis of the casing, a leading edge surface of the flow disrupting feature splaying radially outward in a direction away from the central axis of the casing and forming an obtuse angle with the portion of the casing parallel with the central axis of the casing, and a second face of the flow disrupting feature, between the leading edge surface and a trailing edge of the flow disrupting feature, angled radially inward in a direction toward the central axis of the casing.

17. The turbocharger of claim 16 , wherein the annular flow disrupting feature continuously transitions from upstream to downstream, the leading edge surface of the annular flow disrupting feature forming an upstream transitional portion and the second face between the leading edge surface and the trailing edge of the annular flow disrupting feature forming a downstream transitional portion.

18. The turbocharger of claim 16 , wherein the trailing edge of the annular flow disrupting feature is located substantially in line axially to the leading edge of the at least one main blade.

19. The turbocharger of claim 16 , wherein the annular flow disrupting feature is in an area of the flow passage that is closed to upstream communication with the flow passage except via the flow passage.

20. The turbocharger of claim 16 , wherein an acute angle is formed between the leading edge surface of the flow disrupting feature and the second face between the leading edge surface and the trailing edge of the flow disrupting feature.

21. A turbocharger comprising:
a compressor wheel located in a casing having main blades and configured to rotate within the casing to compress inlet air;
a passage within the casing configured to pass inlet air having a substantially continuous inner surface; and
an annular feature disrupting the continuity of the inner surface located at a leading edge of the main blades;
wherein a leading edge surface of the annular feature splays radially outward, in a direction away from a central axis of the casing, at an obtuse angle from a surface of the casing, a trailing edge of the annular feature located substantially in line axially with the leading edge of the main blades.

22. The turbocharger of claim 21 , wherein the passage is closed to upstream communication at the annular feature except via the passage.

23. The turbocharger of claim 21 , wherein a most upstream portion of the casing is angled inward in a direction towards the central axis of the casing, and wherein a portion of the casing located upstream of the annular feature and downstream of the most upstream portion of the casing is parallel to the central axis of the casing.

24. The turbocharger of claim 21 , wherein the annular feature continuously transitions from upstream to downstream, the leading edge surface of the annular feature forming an upstream transitional portion and a step face between the leading edge surface and the trailing edge of the annular feature forming a downstream transitional portion.

25. The turbocharger of claim 21 , wherein an acute angle is formed between the leading edge surface of the annular feature and a step face between the leading edge surface and the trailing edge of the annular feature, the step face angled r

Assignees

• Karim Ahsanul
• Lizotte Brian W
• Miazgowicz Keith D
• Zouani Abdelkrim
• Ford Global Tech Llc

Inventors

• Karim Ahsanul
• Lizotte Brian W
• Miazgowicz Keith D
• Zouani Abdelkrim

Classifications

• F05D2220/40

  in turbochargers · CPC title

• F04D29/665

  by means of resonance chambers or interference · CPC title

• F04D29/4213

  suction ports · CPC title

• F04D29/667

  by influencing the flow pattern, e.g. suppression of turbulence · CPC title

• F04D29/663 Primary

  Sound attenuation · CPC title